Cooling system for internal combustion engines



June 30, 1942. H. cARosELLl 2,288,514

COOLING SYSTEM FOR INTERNAL COMBUSTION ENGINES Filed Dec. 16, 1939 2Sheets-Sheet 2 June 30, 1942- H. cARosi-:LU

COOLING SYSTEM FOR INTERNAL GOMBUSTION ENGINES 2 Sheets-Sheet l FiledDec. 16, 1939 nga Patented June 30, 1942 COOLING `SYSTEM FOR'INTERNALCMBUSTIGN ENGINES Hellmut Caroselii, Berlin-Adlershof, GermanyApplication December 16, 1939, Serial No. 309,683 In Germany December22, 1938 (Cl. 12S-174) Claims.

This invention relates to Cooling systems in in ternal combustionengines and more particularly to cooling systems for motors in airplanesin which the cooling is effected by liquid means exclusively, In orderto render the invention clearly to be understood it must be pointed out,that cooling systems substantially of the kind referred to mostlyconsist of a chief system and of an auxiliary system. Substantially themain system comprises the pump for moving the cooling means, the coolingjacket of the engine, the radiator proper as well as the requisite pipelines, and the auxiliary system comprises a storage tank as well as thenecessary supply and discharge pipe lines. In order to ensure acontinuous circulation of the cooling agent and a uniform withdrawal ofheat, an ebullition of the cooling agent Within the cooling jacket mustbe avoided. Furthermore, an interruption of the current of the coolingagent Within the suction branch pipe of the pump must be prevented, andnally steam and gas bubbles perhaps emanating from the cooling agentmust be separated from said current.

The first requirement is fuliilled by the cooling systems known up tothe present in that the highest cooling temperature of the cooling uidoccurring, that is the temperature ci the cooling agent at the point ofdischarge from the motor, lies a few degrees, for instance 6 degreescentigrade, below the temperature of steam saturation belonging to thepressure prevailing there.

The second requirement is ensured, when the pressure ahead of the pumpfor the cooling agent is higher by a suiiicient minimum, for instance0.2 atmosphere than the steam pressure belonging to the temperatureprevailing there. For the purpose of separating the steam and gas,devices of varying construction are known. The said devices are soarranged that the steam and gas bubbles separated out are conducted intothe gas chamber of the storage tank.

In respect of a normal system of cooling the following values forinstance, are obtained for In this instance the requirements called forabove are fullled. But there will be difculties if with respect to ahigh drop of heat within the radiator, the temperatures of the coolingagent must be chosen very high, and when theipressure at the dischargepoint of the-cooling agent in the motor or the pressure at the suctionbranch of the pump respectively, in consequence of externalconditions-ior instance at a slight outside pressure particularly duringthe operation at great altitudesis not greater-or even less than thesteam pressure belonging to the temperature of the cooling agent. If inthese instances-for considerations of space and weight-the requiredpressure within the outer branch of the cooling system cannot beproduced statically throughasuperimposed water column, the abovementioned requirements cannot be fulfilled without special auxiliarydevices.

Therefore it is the object of the invention, to obtain an increase ofthe pressure in the main system. This increase of pressure is obtainedby means of one or more'vortex vessels, which are connected to the mainsystem in such a manner, that the cooling agent from the main systementers tangentially into the boundary zone of the spinning vortex ofliquid within the vortex vessel and it will leave said boundary zone ina similar manner.

A further characteristic feature of the invention is to be seen in thatthe auxiliary system is substantially connected with the center of thevortex vessel, so that the supply of cooling agent from the storage tankto the vortex vessel is effected substantially in the inner zone throughstatic pressure. i

A still further characteristic feature of the invention lies in the factthat the said vortex vessels will act as steam separators. In order toobtain such action, the central zone of the vortex Vessel or vortexvessels is connected to the liquid chamber and the steam chamber of thestorage tank by means of separate channels.

A number of modifications according to the invention is shown in thedrawings by way of example.

Figures l, 2a, 2b, 3, Ll and 5 show a modification` ranged behind thedischarge end of the coolingY jacket B, and the conduit I enters saidvortex vessel in such a manner that the conduit will branch off from theboundary zone of the vortex. For that purpose the said conduit I entersthe vortex vessel tangentially (see Figures 2a and 2b) and it leavessaid vessel again in a tangential direction.

The storage tank C is connected to the vortex vessel by means of theconduit 2, which enters the central zone of the vortex vessel 3. In thismanner a higher pressure is obtained within the system I than within thesystem 2, so that the -system I may be considered as the high pressuresystem and the system 2 as the low pressure system.

In lieu of the vortex vessel 3 there may be also employed a mechanicallyacting device, as for instance a driven blade Wheel. By this means thepressure effected through the rotating vortex may be increased withinthe vessel 3.

In order to replenish the quantities of liquid evaporated from thestorage tank C, the vortex vessel 3 must be arranged below the saidtank, so that the liquid will freely flow into the vortex vessel throughthe conduit 2. The said vortex vessel may serve at the same time assteam and air separator. The gas bubbles collecting in the center of thevortex will rise through the conduit 2 into the collecting reservoir.

Figure 3 shows an arrangement in which the movement of the countercurrents of gas and liquid in the conduit 2 is facilitated in that thisconduit consists of two pipes 4 and 5, with the pipe 5 located withinthe pipe 4. The pipe 5 connects the inner Zone with the steam chamber ofthe storage vessel C, while the pipe 4 connects the inner Zone of thevortex vessel 3 with the liquid chamber of the storage vessel C.

In Figure 4 the liquid conduit I between the center of the vortex andthe storage tank and the gas conduit 5 are separated through a two-sidedtapping of the center of the vortex.

Figure 5 shows an arrangement in which the storage tank C is locatedbelow the discharge point of the cooling agent from the motor, as suchis customary in many cases with motors in airplanes for the sake ofsaving space. In order to render possible a ventilation of the coolingsystem at the highest place, which lies in this instance at thedischarge point of the cooling agent, a vortex vessel 6 serving as gasseparator is provided, in which the main conduit I enters and leaves atthe periphery, while the ventilation conduit 5 starts from the centerthereof. A second vortex vessel 3 is arranged according to Figure 4.From this vessel a Ventilating duct may be passed by way of the vortexVessel B to the container C. In the high pressure circuit I both vesselsare arranged in succession. In the upside-down position of the motor thevortex vessels 3 and 6 will change their action. Such vortex vessels maybe arranged at all those points where a ventilation of the coolingsystem appears necessary.

Each Vortex vessel may be made integral with its adjacent part of thecooling system, for instance with the motor or storage tank.

The dimensions of the vortex vessels are governed through the pressurenecessary within the high pressure part of the cooling system.

Cooling systems are known, in which vortex vessels of a form similar tothat described above, are used as steam and air separators. However,with cooling systems of that type the storage vessel is located eitherin the main system-denominated as high pressure part in the presentinstanceor in shunt with a communication of the liquid chamber with themain vsystem (Figure 6) in such a manner that through said connectioncooling agent is to flow from the storage tank C to the main system I.As the pressure in the storage tank C at a slight external pressurecannot be continuously higher than the steam pressure of the coolingliquid at the temperature prevailing within the storage tank, thepressure in the main system must be less at the entering point 'I of thesupply line from the storage vessel C than the steam pressure in thecollecting vessel, in order to permit the liquid to flow from the latterto the main system. But as already mentioned above this requirement willcause an interruption of the cooling current at the entry point of thepump; or in consequence of the centrifugal action of the steam-airseparators 3 within the conduit I such a high pressure level isobtained, that ahead of the entry point of the pump there is a pressure,which is higher than the steam pressure. Subsequently the cooling agentis forced from said point I into the storage tank C. In consequence thequantity of gas 8 contained in the storage vessel is pushed into theconduit l by way of the steam-air separator 3.

Thus the steam-air separator in this arrangement will be unsuccessful.

The novel feature over this known arrangement, as stated above, consistsin that both the liquid chamber and the gas chamber of the of thestorage tank are in communication with the center of the vortex vessel,which is under a slight pressure only.

I claim:

l. Cooling system for internal combustion engines particularly formotors in airplanes in which the cooling is effected by liquid meanscomprising in combination: a main system consisting substantially of apump for the liquid, a cooling jacket for the engine, a radiator andpipe lines connecting said pump, jacket and radiator, an auxiliarysystem consisting substantially of a storage tank and supply anddischarge pipe lines connected to said storage tank and means connectingsaid supply and discharge pipe lines to said main system for maintainingin said main system a higher pressure than in the auxiliary system, saidmeans comprising a cylindrical vortex vessel having tangentialconnections to the main system and a connection to said supply pipe at apoint of reduced pressure in the vortex vessel.

2. Cooling system for internal combustion engines particularly formotors in airplanes in which the cooling is effected by liquid meanscomprising in combination: a main system consisting substantially of apump for the liquid, a cooling jacket for the engine, a radiator andpipe lines connecting said pump, jacket and radiator; an auxiliarysystem consisting substantially of a storage tank and supply anddischarge pipe lines connected to said storage tank and means connectingsaid supply and discharge pipe lines to said main system for maintainingin said main system a higher pressure than in the auxiliary system, saidmeans comprising a cylindrical vortex vessel having at its endstangential connections to the main system and axial connections to saidsupply and discharge pipes of said auxiliary system.

3. Cooling system for internal combustion engines particularly formotors in airplanes in which the cooling is effected by liquid meanscompris'- ing in combination: a main system consisting substantially ofa pump for the liquid, a cooling jacket for the engine, a radiator andpipe lines connecting said pump, jacket and radiator; an auxiliarysystem consisting substantially of a storage tank and supply anddischarge pipe lines connected to said storage tank and means connectingsaid supply and discharge pipe lines to said main system for maintainingtherein a higher pressure than in the auxiliary system, said meanscomprising a cylindrical vortex Vessel having at its ends tangentialconnections to the main system and a connection to the supply pipe ofthe auxiliary system extending axially from an end thereof.

4. Cooling system for internal combustion engines particularly formotors in airplanes in which the cooling is effected by liquid meanscomprising in combination; a main system consisting substantially of apump for the liquid, a cooling jacket for the engine, a radiator andpipe lines connecting said pump, jacket and radiator, an auxiliarysystem consisting substantially ol a storage tank and supply anddischarge pipe lines connected to said storage tank and means connectingsaid supply and discharge pipe lines to said main system for maintainingtherein a higher pressure than in the auxiliary system, said meanscomprising a cylindrical vortex vessel having at its ends tangentialconnections to the main system and an axial connection to the supplypipe from the storage tank of the auxiliary system from a point ofreduced pressure in the vortex vessel.

5. Cooling system for internal combustion engines particularly formotors in airplanes in which the cooling is eifected by liquid meanscomprising in combination: a main system consisting substantially of apump for the liquid, a cooling jacket for the engine, a radiator andpipe lines connecting said pump, jacket and radiator; an auxiliarysystem consisting substantially of a storage tank and supply anddischarge pipe lines connected to said storage tank and means connectingsaid supply and discharge pipe lines to said main system for maintainingtherein a higher pressure than in the auxiliary system, said Ymeanscomprising a cylindrical vortex vessel having tangential connections tothe main system and axial connections with said discharge and supplypipes, said pipes terminating in the steam chamber and the liquidchamber of the storage tank, respectively.

6. Cooling system for internal combustion engines particularly formotors in airplanes in which the cooling is effected by liquid meanscomprising in combination: a main system consisting substantially of apump for the liquid, a cooling jacket for the engine, a radiator andpipe lines connecting said pump, jacket and radiator; an auxiliarysystem consisting substantially of a storage tank and supply anddischarge pipe lines connected to said storage tank and a cylindricalvortex vessel having co-axial connections with said supply and dischargepipe lines and tangential connections With said main system forproducing a higher pressure in the main system than in the auxiliarysystem, said vortex vessel effecting a separation of gas and steam fromthe liquid.

7. Cooling system for internal combustion engines particularly formotors in airplanes in which the cooling is effected by liquid meanscomprising in combination: a main system consisting substantially of apump for the liquid, a

cooling jacket for the engine, a radiator and pipe lines connecting saidpump, jacket and radiator; an auxiliary system consisting substantiallyof a storage tank and supply and discharge pipe lines connected to saidstorage tank and cylindrical vortex Vessels having axial connections tosaid supply and discharge pipe lines and tangential connections to saidmain system for producing a higher pressure in the main system than inthe auxiliary system.

8. Cooling system for internal combustion engines` particularly formotors in airplanes in which the cooling is effected by liquid meanscomprising in combination: a main system consisting substantially of apump for the liquid, a cooling jacket for the engine, a radiator andpipe lines connecting said pump, jack and radiator; an auxiliary systemconsisting substantially of a storage tank and supply and discharge pipelines connected to said storage tank, means connecting said supply anddischarge pipe lines to said main system for maintaining a higherpressure in the main system than in the auxiliary system, said meanscomprising cylindrical vortex vessels arranged so the functions of saidsupply and discharge pipe lines can be automatically interchanged, saidvortex vessels having the connections to the main system effectedtangentially and in succession and having their central Zones connectedwith the storage tank by said supply and discharge pipes.

9. Cooling system for internal combustion engines particularly formotors in airplanes in which the cooling is elected by liquid meanscomprising in combination: a main system consisting substantially of apump for the liquid, a cooling jacket for the engine, a radiator andpipe lines connecting said pump, jacket and radiator; an auxiliarysystem consisting substantially of a storage tank and supply anddischarge pipe lines connected to said storage tank; means connectingsaid supply and discharge pipe lines to said main system for maintaininga higher pressure in the main system than in the auxiliary system, saidmeans comprising cylindrical vortex vessels arranged so the functions ofsaid supply and discharge pipe lines can be automatically interchanged,said Vortex vessels having the connections to the main system effectedtangentially and in succession and the central zones thereof connectedwith the storage tank by said supply and discharge pipes, the vortexvessel serving for the separation of gas and steam from the liquid beinglocated above the storage tank and the vortex vessel serving for theproduction of the pressure proper being arranged below the said storagetank.

10. Cooling system for internal combustion engines particularly formotors in airplanes in which the cooling is effected by liquid meanscomprising in combination: a main system consisting substantially of apump for the liquid, a cooling jacket for the engine, a radiator andpipe lines connecting said pump, jacket and radiator: an auxiliarysystem consisting substantially of a storage tank and supply anddischarge pipe lines connected to said storage tank and means connectingsaid supply and discharge pipe lines to said main system for maintainingtherein a higher pressure than in the auxiliary system, said meansconsisting of a cylindrical vortex vessel having tangential connectionswith the main system and axial connections with the auxiliary system atits central zone of reduced pressure.

HELLMUT CAROSELLI'

